EP3323721A1 - Principe pour la formation de corps et de contours avantageusement aérodynamiques de dispositifs d'aéronefs et utilisation de la technologie furtive - Google Patents

Principe pour la formation de corps et de contours avantageusement aérodynamiques de dispositifs d'aéronefs et utilisation de la technologie furtive Download PDF

Info

Publication number
EP3323721A1
EP3323721A1 EP17150368.3A EP17150368A EP3323721A1 EP 3323721 A1 EP3323721 A1 EP 3323721A1 EP 17150368 A EP17150368 A EP 17150368A EP 3323721 A1 EP3323721 A1 EP 3323721A1
Authority
EP
European Patent Office
Prior art keywords
aircraft
radio
radiation
aircraft part
part according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP17150368.3A
Other languages
German (de)
English (en)
Inventor
Anton Alexandrovich Shchukin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Publication of EP3323721A1 publication Critical patent/EP3323721A1/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K9/00—Screening of apparatus or components against electric or magnetic fields
    • H05K9/0007—Casings
    • H05K9/0045—Casings being rigid plastic containers having a coating of shielding material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H3/00—Camouflage, i.e. means or methods for concealment or disguise

Definitions

  • Stealth airplane or stealth aircraft is the name given to an aircraft using stealth technology. This is done by means of special geometric shape and the surface condition, so that the aircraft is to be detected for a radar only at short distances.
  • Electromagnetic waves are usually provided by special electronics.
  • the outer shape also contributes significantly to the fact that less electromagnetic waves are reflected than in conventional aircraft.
  • special radar-absorbing materials RAM
  • RAM radar-absorbing materials
  • particularly quiet engines are used. The exhaust jet of these engines is kept cool by special precautions and escapes to the ground shielded to provide infrared detectors as low as possible infrared signature.
  • composite materials instead of metal ensures a low radar signature.
  • the invention relates to an aircraft or aircraft part, characterized in that the outer surface of the aircraft or aircraft part is made of radio- and / or radiation-transparent material and on the inside of the A coating of radio and / or radiation-reflecting material is arranged aircraft or aircraft part.
  • the given principle of production of aircraft or aircraft parts makes it possible to arrange the reflection surfaces in the interior of the aircraft or of the aircraft part, namely inside a radio-transparent body of the aircraft.
  • the invention makes it possible to protect the high-reflection surfaces from physical or other external influences. Dirt particles that accumulate on the surface of the aircraft, especially during take-off and landing, no longer have a disturbing effect on the reflection surfaces, since these are protected inside.
  • the aircraft or aircraft parts according to the invention have two profiles: an outer and an inner.
  • the outer profile is designed to provide the aerodynamically advantageous properties and is made of radio-transparent material.
  • the inner profile is constructed to have the most efficient radio-reflecting shape and is coated with radio-reflective material.
  • this may be a wing made of a radio-transparent carbon compound, wherein the outer profile meets the aerodynamic requirements, while the inner profile meets the requirements for ensuring the radioelectronic invisibility.
  • radio-emitting elements and / or mechanisms are arranged in the interior of the aircraft or aircraft part.
  • the inside of the aircraft or aircraft part is additionally coated with one or more protective layers.
  • the radiation-reflecting layer protects against mechanical damage.
  • the radio-transparent material comprises a carbon compound.
  • the invention relates to the use of a described aircraft or aircraft part to create a radio-opaque interior volume.
  • the invention provides a principle for the design of an aerodynamically advantageous body of an aircraft (e.g., hull) or an element or portion thereof, or an aircraft device, which parts are made of radio-transparent materials.
  • aircraft parts can be provided which have a desirable and advantageous contour for the reflection of radio or radio radiation.
  • the aircraft part comprises one or more radioreflective materials.
  • the invention thus enables necessary or optional aircraft mechanisms and devices to be located in a zone that is completely protected from locating radiation or other radiation.
  • the profile of the aircraft or aircraft part (e.g., the aircraft wing) is designed so that the outside is maximally aerodynamically advantageous and it is made of a radio-transparent material, e.g. a composite.
  • the composite must provide certain strength properties and other properties that are optimal for the design of the given device. A person skilled in the art knows how to select this material without being inventive himself.
  • a profile is formed with properties that allow an interior space which optimally reflects certain radiation.
  • the walls of this interior are coated for this with a radioreflective material (for example, by means of the reaction of a silver mirror, or by a coating with plates of a suitable material).
  • a radioreflective material for example, by means of the reaction of a silver mirror, or by a coating with plates of a suitable material.
  • this "mirror layer" is additionally covered by one or more protective layers.
  • protective layers The person skilled in the art knows in which cases a coating with additional substances may be necessary without being inventive in the process.
  • the reflection coefficient may be close to one, so that the radiation exposure of the internal devices and mechanisms is completely prevented, and as a result, the reflection of this radiation from these devices and mechanisms are prevented, such reflected radiation not prone to detection are. Above this, radiation from the interior does not escape to the outside.
  • aircraft components e.g. Aircraft wings, the fuselage, tail units, the tail of the aircraft, other mechanical components, hanging containers and all other parts, components or accessories of an aircraft.
  • the radiation-reflecting coating additionally protects the aircraft part from mechanical damage.
  • radio- or radio-emitting and radio- or radio-receiving elements of mechanisms or devices can be arranged outside the radiation-tight body.
  • FIG. 1 shows a schematic representation of an aircraft wing in a preferred embodiment of the invention.
  • the aircraft wing comprises radiotransparent material 1. In addition, it has an aerodynamically advantageous shape 2.
  • a radiation reflective coating 3 is applied to the inner surface of the blade.
  • the interior 4 of the wing is protected from radiation 6.
  • Devices and mechanisms 5 are protected Interior 4 of the wing arranged. Locating radiations or other radiations 6 are sent back as reflected radiation 7.

Landscapes

  • Engineering & Computer Science (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Details Of Aerials (AREA)
EP17150368.3A 2016-11-21 2017-01-05 Principe pour la formation de corps et de contours avantageusement aérodynamiques de dispositifs d'aéronefs et utilisation de la technologie furtive Withdrawn EP3323721A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16199727 2016-11-21

Publications (1)

Publication Number Publication Date
EP3323721A1 true EP3323721A1 (fr) 2018-05-23

Family

ID=57389252

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17150368.3A Withdrawn EP3323721A1 (fr) 2016-11-21 2017-01-05 Principe pour la formation de corps et de contours avantageusement aérodynamiques de dispositifs d'aéronefs et utilisation de la technologie furtive

Country Status (1)

Country Link
EP (1) EP3323721A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018121826A1 (de) * 2018-09-07 2020-03-12 Airbus Defence and Space GmbH Vorrichtung zum Filtern von elektromagnetischer Strahlung, Luft- und Raumfahrzeug und Verfahren zum Herstellen der Vorrichtung

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4924228A (en) * 1963-07-17 1990-05-08 Boeing Company Aircraft construction
DE4007986C1 (en) * 1990-03-13 1991-09-19 Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De Aircraft structure with cavities - filled with material absorbing or reflecting radar vanes for camouflage or imaging
US20150329200A1 (en) * 2012-12-31 2015-11-19 University Of Kansas Radar energy absorbing deformable low drag vortex generator
EP3045385A1 (fr) * 2015-01-19 2016-07-20 Mitsubishi Aircraft Corporation Machine de transport

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4924228A (en) * 1963-07-17 1990-05-08 Boeing Company Aircraft construction
DE4007986C1 (en) * 1990-03-13 1991-09-19 Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De Aircraft structure with cavities - filled with material absorbing or reflecting radar vanes for camouflage or imaging
US20150329200A1 (en) * 2012-12-31 2015-11-19 University Of Kansas Radar energy absorbing deformable low drag vortex generator
EP3045385A1 (fr) * 2015-01-19 2016-07-20 Mitsubishi Aircraft Corporation Machine de transport

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018121826A1 (de) * 2018-09-07 2020-03-12 Airbus Defence and Space GmbH Vorrichtung zum Filtern von elektromagnetischer Strahlung, Luft- und Raumfahrzeug und Verfahren zum Herstellen der Vorrichtung

Similar Documents

Publication Publication Date Title
EP2532588B1 (fr) Aéronef camouflé
DE202007001565U1 (de) Panzerscheibe
EP1816070A2 (fr) Corps d'aéronef et son procédé de fabrication
DE102005060958A1 (de) Schutzvorrichtung
DE102010003817A1 (de) Werkstücküberzug und damit überzogenes Werkstück
EP3323721A1 (fr) Principe pour la formation de corps et de contours avantageusement aérodynamiques de dispositifs d'aéronefs et utilisation de la technologie furtive
DE60129671T2 (de) Verbessertes kunstflugzeug
DE10046568A1 (de) Flugzeugtürfenster eines Verkehrsflugzeuges
DE102007022616C5 (de) Mehrschichtplatte mit schräger Schlitzung des Plattenkerns zur Reduzierung der Körperschallabstrahlung und zur Erhöhung der Schalldämmung bei Beibehalten der mechanischen Stabilität
DE3821588C1 (de) Flügelblatt mit schwachem Radarecho
DE102015117401A1 (de) Flugzeugkabinenanordnung
CH636437A5 (en) Artillery round having a radar reflector
DE1800848C3 (de) Geschweißtes Panzergehäuse
EP1586501A1 (fr) Revêtement pour cabine d'aéronef
DE2855564A1 (de) Werkstueckpalette
DE3426990C2 (de) Radarschutz an einem Fluggerät
DE102014004838A1 (de) Effektor mit abwerfbarer Tarnschale
DE102019129507A1 (de) Radom für einen Radarsensor eines Kraftfahrzeugs und Kraftfahrzeug
DE102011004844A1 (de) Türrahmenverbund, Rumpfabschnitt sowie Luft- oder Raumfahrzeug
DE3542614A1 (de) Verfahren zur daempfung von optischen substratwellen in einem integriert optischen bauelement
DE102015119396A1 (de) Verbundbauteil und Verfahren zur Herstellung eines Verbundbauteils
DE977525C (de) Interferenzabsorber fuer Funkwellen als Radartarnung fuer Start- und Landebahnen
EP0531913B1 (fr) Véhicule avec vitrage armé
DE4305010C2 (de) Anordnung zur Radartarnung von Flugkörpern
EP4043192A1 (fr) Patch de réparation rapide permettant de réparer des dommages extérieurs, ainsi que procédé de réparation rapide

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20181124